System and method for cooling the brakes of landing gear of an aircraft

Abstract

A system for cooling the brakes of a brake system of a landing gear of an aircraft, including: a compressor configured to generate a pressurized airflow, the compressor including at least one air outlet, and an air jet pump including: a pump tube including a first end connected to the air outlet and a second end, the pump tube being designed to carry the pressurized airflow between the first and second ends, and a plurality of injectors connected to the second end of the pump tube, and configured to inject the pressurized airflow.

The invention claimed is: 
     
       1. A cooling system for cooling brakes of a brake system of a landing gear of an aircraft, comprising:
 a compressor configured to generate a pressurized air flow, said compressor comprising at least one air outlet, and 
 an air jet pump comprising:
 a pump tube comprising a first end connected to said air outlet and a second end, said pump tube being designed to convey said pressurized air flow between the first and second ends, and 
 a plurality of injectors connected to said second end of the pump tube, and configured to inject said pressurized air flow, 
 
 wherein the plurality of injectors comprises a central injector arranged as an extension of the second end of the pump tube and a plurality of intermediate injectors arranged 360º around said central injector. 
 
     
     
       2. The cooling system according to  claim 1 , wherein each injector has a cross-sectional restriction along a path of the pressurized air flow. 
     
     
       3. The cooling system according to  claim 1 , wherein the plurality of injectors are arranged circumferentially and centred on the second end of the pump tube. 
     
     
       4. The cooling system according to  claim 1 , wherein the plurality of injectors comprises a plurality of external injectors arranged 360° around said intermediate injectors. 
     
     
       5. The cooling system according to  claim 4 , wherein the plurality of external injectors and the plurality of intermediate injectors are arranged in a staggered pattern around the second end of the pump tube. 
     
     
       6. The cooling system according to  claim 1 , wherein at least one or each injector is elbow shaped. 
     
     
       7. The cooling system according to  claim 1 , wherein the compressor is an electric compressor. 
     
     
       8. A landing gear of an aircraft comprising:
 at least one wheel; 
 a brake system comprising brakes adapted to slow or stop the rotation of said at least one wheel; and 
 a cooling system according to  claim 1 . 
 
     
     
       9. The landing gear according to  claim 8 , wherein the compressor of the cooling system is arranged remotely from an area near the brakes. 
     
     
       10. The landing gear according to  claim 8 , wherein each injector is arranged outside a rim of the wheel. 
     
     
       11. The landing gear according to  claim 8 , wherein each injector is arranged inside a rim of the wheel. 
     
     
       12. A method for cooling the brakes of a brake system of a landing gear of an aircraft, the landing gear including at least one wheel, a brake system comprising brakes adapted to slow or stop the rotation of said at least one wheel, and a cooling system according to  claim 1 , the method comprising:
 compressing, by the compressor, an air flow so as to generate a pressurized air flow; 
 conveying the pressurized air flow, by the pump tube, to an area near the brakes; 
 injecting, by each injector, the pressurized air flow into said area near the brakes; and 
 sucking an air flow from said area near the brakes.